https://doi.org/10.1140/epjs/s11734-025-01937-w
Regular Article
Scaling methodology to predict low bypass turbofan engine performance
Department of Aerospace Engineering, Indian Institute of Technology Kanpur, 208016, Kanpur, Uttar Pradesh, India
Received:
7
July
2025
Accepted:
5
September
2025
Published online:
15
September
2025
In the present work, a universal methodology is proposed for predicting the performance of mixed-flow low-bypass turbofan engines, which may also be applied to other classes of gas turbine engines. The available design-point performance in conjunction with the basic engine dimensions are mapped and subsequently the off-design performance is determined by applying scaling laws to a mini turbojet engine. This approach emphasizes scaling the compressor performance and deriving the associated flow parameters, which are then used to estimate engine behavior under varying operating conditions. The engine performance at different RPM settings within the envisaged flight envelope is evaluated across a range of Mach numbers and altitudes. To establish general predictive relations, the resulting performance parameters are expressed as functions of Mach number and altitude using linear regression. This methodology provides a rational starting point for performance evaluation and flight testing, offering a preliminary yet cost-effective means of assessing engine behavior within a targeted flight envelope. The robustness of the proposed methodology is validated using experimental data from a mini turbojet engine, while systematically integrating existing studies and literature to predict the performance of the target engine. Standard one-dimensional flow equations are utilized to derive flow parameters at various stations within the turbofan engine, while GasTurb 14 is employed to supplement and validate the predictions. In the present work, a framework is proposed for a universal methodology for performance prediction, initially demonstrated on mixed-flow low-bypass turbofan engines but generalizable to all classes of gas turbine engines, thereby enhancing its applicability and robustness.
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© The Author(s), under exclusive licence to EDP Sciences, Springer-Verlag GmbH Germany, part of Springer Nature 2025
Springer Nature or its licensor (e.g. a society or other partner) holds exclusive rights to this article under a publishing agreement with the author(s) or other rightsholder(s); author self-archiving of the accepted manuscript version of this article is solely governed by the terms of such publishing agreement and applicable law.
